gemini 3 flight press kit
DESCRIPTION
1st Gemini manned mission.TRANSCRIPT
WO 1-4155 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASt-lINGTON. D C 20546 TELS W O 3-6915
FOR RELEASE: Wednesday A M s March 17. 1965
RELEASE NO: 65-81
R E S S
PROJECT: GEMINI-TITAN 3
GENERAL NEWS RELEASE ............................. 1-4
TECHNICAL BACKGROUND Primary Objectives ............................. 5 Secondary Objectives ........................... 6 Mission Description ............................ 7 Flight Data .................................... 8
8 Weather Requirements ........................... Countdown ...................................... 10
11a Summary Flight Plan ............................ I;il.unch ......................................... 12 In-Flight ...................................... 14 Reentry. Landing. Recovery ..................... 15 Abort Modes .................................... 1gA Spacecraft Landing Sequence .................... 19B Manned Space Flight Tracking Network ........... 20 Network Responsibility ......................... 23 Network Configuration. Capability, ............. 25A Experiments .................................... 26 Reentry Communications ........................ 26 Sea Urchin Egg ................................ 28 White Blood Cells ............................. 2 9 Cardiovascular Effects ........................ 30 Medical Checks ................................ 32 Photography ................................... 32 Food Evaluation ............................... 32
Gemini Survival Package ........................ 35 Gemini Spacecraft .............................. 37 Gemini Launch Vehicle .......................... 39 Gemini Space Suit .............................. 41 Crew Biographies ............................... 43 Virgil I . "Gus" Grissom ....................... 43 John W . Young ................................. 45
Schirra. Jr ......................... 46 Thomas P . Stafford ............................ 48 project Officials .............................. 50
Meals ......................................... 34
Walter M . GT-3 Information Mission Organization.. ........ ~ O A
Launch scheduled no ear l ier than March 22. 1965
WO 2-41 5 5 N E W S WASHINGTON, D.C. 20546 TELS' WO 3-692 5 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
FOR RELEASE: WEDNESDAY A M ' S March 17, 1965
RELEASE NO: 65-81
NASA SCHEDULES FIRST
MANNED GEMINI FLIGHT
FROM CAPE KENNEDY
The f i r s t United S t a t e s two-man space f l i g h t i n a
Gemini Spacecraft i s scheduled t o be launched from Cape
Kennedy no e a r l i e r than March 22, the National Aeronautics
and Space Administration announced today.
Astronauts V i r g i l I. (Gus) Gr i s som and John Young make
up the crew f o r the th ree -o rb i t f l i g h t .
M. Schirra , Jr., and Thomas P. S ta f ford a r e the backup crew.
They w i l l r ep lace the prime crew should e i t h e r member of t ha t
team become i n e l i g i b l e f o r medical o r o the r reasons.
Astronauts Walter
T h i s f i r s t manned f l i g h t i n a Gemini spacecraf t i s
designated Gemini-Titan 3 o r GT-3 - Gemini f o r the spacecraf t ,
T i t an I1 f o r t he launch vehicle .
A successfu l GT-3 f l i g h t w i l l achieve many s i g n i f i c a n t
f i rs ts f o r United S t a t e s manned space f l i g h t program:
-- The f i r s t maneuvering o r change of o r b i t a l plane by
the crew.
-- U s e of a va r i ab le lift c a p a b i l i t y by the crew during
r e e n t r y t o "f ly" t o a se l ec t ed landing area. . *
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The spacec ra f t w i l l be launched by a two-stage Ti tan 11, *
a modif ied U.S. A i r Force ICBM, i n t o a 100-150 mile o r b i t .
I t ' s o r b i t w i l l t ake about 90 minutes ( o r b i t a l per iod) and
range between 33 degrees nor th and south of the equator.
To ta l f l i g h t t i m e i s expected t o be about fou r hours and
50 minutes -- from l i f t - o f f t o landing i n the At l an t i c Ocean
near Grand Turk I s l and i n the West Indies .
The f irst maneuver w i l l take p lace near completion of
the f i r s t o r b i t as the spacecraf t passes over Texas. Small
rockets , c a l l e d t h r u s t e r s , w i l l be f i r e d t o change the o r b i t
to near c i r c u l a q a b o u t 100-107 miles. On the second o r b i t
t he t h r u s t e r s w i l l be f i r ed i n a l a t e r a l d i r e c t i o n causing
a s l i g h t s h i f t In o r b i t a l plane angle. They w i l l be f i r ed i n
a r e t r o d i r e c t i o n again on the t h i r d o r b i t r e s u l t i n g i n an
e l l i p t i c a l o r b i t with a low po in t of about 52 miles.
Af te r f i r i n g t h e r e t r o rocke ts i n the f r i n g e s of Earth's
atmosphere, the a s t ronau t s begin t h e i r cont ro l led r een t ry t o
the prescr ibed landing po in t and recovery by U.S. Naval forces .
Three i n - f l i g h t s c i e n t i f i c experiments are planned for
the GT-3 mission. One experiment w i l l t e s t e f f e c t s of
weightlessness on l i v i n g c e l l s . Another w i l l measure the
e f f e c t of weightlessness and r a d i a t i o n on human white blood
c e l l s .
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* All miles given are s t a t u t e
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I n a t h i r d experiment, t he spacecraf t w i l l e j e c t water
i n t o the plasma sheath that surrounds i t during re-entry
and r ad io s i g n a l s w i l l be d i r ec t ed through the sheath.
Normally, t h i s plasma sheath, an ionized l aye r of a i r , causes
r ad io blackout ,
The study of cardiovascular e f f e c t s of space f l i g h t
which began i n Pro jec t Mercury w i l l be continued.
Space food experiments, a l s o begun i n ProJec t Mercury,
w i l l be c a r r i e d out on the second o r b i t . Two meals, each
containing freeze-dry foods and two bi te -s ized items, w i l l
be ca r r i ed on the f l i g h t . A water gun device w i l l be used
f o r rehydrat ing the food and drinking.
Gemini i s the second phase of America's manned space
f l i g h t program, It w i l l provide experience i n o r b i t a l
maneuvers, permit long dura t ion f l i g h t s l a s t i n g up t o 14 days
and be a vehic le f o r manned s c i e n t i f i c i nves t iga t ions i n space,
Gemini i s named a f t e r t he c o n s t e l l a t i o n containing the
twin stars Cas tor and P o l l u x .
GT-3 fo l lows two successfu l unmanned Gemini Launches.
GT-1 was launched i n t o o r b i t Apr, 8, 1964, i n a te,st of
booster and guidance systems and proved s t ruc tura l i n t e g r i t y
of the spacec ra f t and booster. GT-2, a sub-orb i ta l f l i g h t
Jan. 29, 1965, tes ted the spacecraf t a t maximum heat ing rates and demonstrated structural integrity and systems performance throughout f l i g h t , r een t ry and parachute water landing.
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Gemini i s under the d i r e c t i o n of the Off ice of Manned
Space Fl ight , NASA Headquarters, Washington, Do C , and is
managed by NASA's Manned Spacecraft Center i n Houston.
Gemini i s a n a t i o n a l space e f f o r t . The p r o j e c t i s
supported by the Department of Defense i n such areas as
booster development, launch operations, t racking and recovery.
(Background information follows)
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GT-3
PRIlvlARY OBTECTIVES
1. Demonstrate manned orbital flight in the Gemini
spacecraft and further qualify spacecraft and launch vehicle
systems f o r future manned missions.
2. Demonstrate and evaluate operations of the world-
wide tracking network with a spacecraft and crew.
3. performance.
Evaluate Gemini design and its effects on crew
4. Demonstrate and evaluate capability to maneuver
the spacecraft in orbit using the Orbital Attitude and
Maneuver System (OAMS) . 5. Demonstrate capability to control the reentry
flight path and the landing point.
6 . Evaluate performance of the following spacecraft
systems:
a.
b.
C.
d.
e.
f.
Crew station controls and displays
Environmental control
Gemini space suits
Guidance and control
Electrical power and sequential
Propulsion
Communications and tracking - more -
- 6 -
h. Pyrotechnics
i. Instrumentation
j.
k. Landing and recovery
Food, water and waste management
7. Demonstrate systems checkout, prelaunch and launch
procedures for manned spacecraft.
8. Recover the spacecraft and evaluate recovery systems,
GT-3
SECONDARY ORJECTIVES
Evaluate the following spacecraft systems: 1.
a. Astronaut equipment
b. Biomedical instrumentation
C. Personal hygiene
2. Execute the following experiments:
a. Sea urchin egg growth
b.
c. Reentry communications
Radiation and zero-g effects on blood
3. Obtain general photographic coverage in orbit,
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- 7 -
M I S S I O N DESCRIPTION
The spacecraf t w i l l be launched from Pad 19 on a
t r u e azimuth heading of 72 degrees e a s t o f nor th ,
Second s tage engine cu tof f w i l l occur about 533 s t a t u t e
miles from Cape Kennedy a t a ve loc i ty of about 17,400 m i l e s
p e r hour. Twenty seconds l a t e r , engine t a i l o f f will increase
the ve loc i ty t o about 17,500 mph, a t which time the crew
w i l l separa te the spacecraf t from the launch vehicle by
f i r i n g the OAMS thrusters.
ve loc i ty and w i l l i n s e r t t he spacecraf t i n t o a 100-150-mile
e l l i p t i c a l o r b i t .
This w i l l add 10 f't/sec t o the
Af t e r one o r b i t , a t about one hour, 30 minutes a f t e r
l i f t - o f f , t he forward-firing OAMS thrusters w i l l be f i r ed t o
provide a 66 f t / sec (45 mph) ve loc i ty change i n an in-plane
re t rograde a t t i t u d e t o put the spacecraf t i n t o a 100-107-
mile o r b i t .
A t two hours, 20 minutes a f t e r l i f t - o f f , during the
second o r b i t , south and nor th out-of-plane burns t o t a l l i n g
14 f t /sec w i l l be performed. Forward-firing t h r u s t e r s w i l l
be used for the 12 f t /sec burn, followed by a 2 f t / sec burn
of the a f t - f i r i n g thrusters.
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FLIGHT DATA
Launch Azimuth -- 72 degrees Flight Duration -- Approximately 4:50 hours Initial Orbital Parameters -- 100-150 and 100-107 miles
Reentry Velocity -- About 24,000 ft/sec, 16,450 mph
Reentry Temperature -- Approximately 3000 degrees Fahrenheit on surface of heat shield
Oxygen -- Primary 15.3 pounds, Secondary 13 pounds
OAMS Fuel -- Approximately 300 pounds
Cabin Environment -- 100 percent oxygen pressurized at 5 psi Retrorockets -- Each of the four retrorockets produces
approximately 2500 pounds of thrust for 5.5 seconds. Will fire separately
Landing Point -- Atlantic Ocean, about 60 miles from Grand Turk Island
WEATHER REQUIREMENTS
Recovery capability is based primarily on reports
from recovery force commanders to the recovery task force
commander at the Mission Control Center.
A weather condition which results in an unsatisfactory
recovery condition in a planned landing area will be
considered as the basis for a hold or a scrub.
are guidelines only, and conditions along the ground track
will be further evaluated prior to and during the mission.
The following
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Launch Area:
Surface winds - 18 knots with gusts to 25 knots.
Ceiling - 5,000 feet cloud base minimum.
Visibility - 6 miles minimum. Wave height - 5 feet maximum,
Planned Landing Areas:
Surface winds - 30 knots maximum.
Ceiling - 1,500 feet cloud base minimum.
Visibility - 6 miles minimwn. Wave height - 8 feet maximum.
Contingency Landing Areas:
Weather and status of contingency recovery forces will
be continually monitored during the countdown and orbital
phases of the mission. Recommendations will be made to the
Mission Director who will make the go-no-go decision based
upon conditions at the time.
Pararescue:
The decision to use pararescue personnel depends upon
weather conditions, surface vessel locations, and the ability
to provide air dropped supplies until the arrival of a surface
vessel. The final decision to jump will be made by the jump-
master. Weather guidelines for pararescue operations are:
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Surface winds - 25 knots maximum.
Cei l ing - 1,000 f e e t cloud base minimum.
V i s i b i l i t y - t a r g e t v i s i b l e .
Waves - 5 f e e t maximwn, swel ls 10 o r 11 f e e t m a x i m u m .
Near the end of t he t h i r d o r b i t , a p re - r e t ro burn o f 93
f t / s ec (63 mph) w i l l be performed with the a f t - f i r i n g
t h r u s t e r s t o put t he spacecraf t i n t o a r e e n t r y e l l i p t i c a l
o r b i t with a per igee o f 52 miles. This maneuver w i l l be
performed west of H a w a i i , 12 minutes p r i o r t o the time the
r e t r o r o c k e t s f i r e f o r r een t ry i n t o the primary landing a rea
near Grand Turk Is land.
R e t r o f i r e i s planned a t fou r hours, 33 minutes and
30 seconds a f t e r l i f t - o f f . The spacec ra f t w i l l land about
20 minutes a f t e r r e t r o f i r e .
T minus one day
T minus 420 minutes
T minus 400 minutes
T minus 380 minutes
T minus 330 minutes
T minus 258 minutes
T minus 220 minutes
COUNTDOWN
Spacecraf t and launch vehic le prelaunch se rv ic ing and checks
Begin countdown
Spacecraf t power on
Gemini launch vehic le (GLV) and spacec ra f t systems Check
spacec ra f t command checks w i t h Mission Control Center
Awaken crew
Spacecraft/computer memory loading
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- 11 - T minus 190 minutes
T minus 173 minutes
T minus 160 minutes
T minus 145 minutes
T minus 100 minutes
T minus 75 minutes
T minus 35 minutes T minus 30 minutes
T minus 20 minutes
T minus 6 minutes
T minus 3 minutes
T minus 0
T plus 1.8 seconds
T plus 3.8 seconds
T plus 4 seconds
Pad clear for GLV ordnance and range command checks
Begin sensor placement and suiting of crew
GLV tanks to launch pressure
Ground test of launch program
Crew enters spacecraft
Spacecraft hatch closure. Dismantle White Room
Erector lowering
Activate all spacecraft communication links
Spacecraft to internal power
GLV-spacecraft final status check
Update GLV launch azimuth and spacecraft computer
Engine start signal
Thrust chamber pressure switch -- calibrated for 77 per cent of rated engine thrust -- is activated, starting a two-second timer.
Spacecraft umbilicals release, GLV tiedown bolts fire
Lift -off
Lift-off plus 2 minutes 36 seconds LO plus 3 minutes 15 seconds
Staging
Fairing jettison
LO plus 5 minutes 38 seconds SECO (Second stage engine cutoff)
Lo plus 5 minutes 58 seconds Separation maneuver. Confirm orbit. - more -
- l l a - GT- 3
SUMMARY FLIGHT PLAN
Launch
I n s e r t i o n Checkl i s t Align Platform
Blood Pressure T/M CalYb
RCS Plume Observation
Catch-up Mode Check
Sea Urchin Egg Exp - Once
GO/NO GO Update f o r T r a n s l a t i o n No. 1
L 30
PI LOT I
Unstow Equipment T r a j e c t o r y Update Communications Check Blood Pressure
Empty Launch Day Urine Bag S u i t I n t e g r i t y Check
Oral Temp
S/C GMT T ime Hack Tra jec tory Update Human Blood I r r a d i a t i o n Exp
S t a r t
Iuman Blood I r r a d i a t i o n . Exp s t o p
GT- 3 SUMMARY FLIGHT PLAN
c i= u-
COMMAND P I LOT I -
Control S/C t o oO, oO, 0'
:'-Translation - NO. 1
-ORBIT 2 Tape Plybk - 1
P l a t f o m Alignment and Caging Check
- 1 Blood pressure - 50
1 - 2
Control S/C t o O o , 180°, 0'
- L O O - - - - - -
I Horizon Scanner Check
Y T s l a t i o n a l Systems Check
- GO NO GO Decision : T r a j e c t o r y Update
- 2 Control S/C t o 90' Yaw
-
Hor Scan Control Mode C h a r a c t e r i s t i c s Check
- 2 - 40 : Align Platform
-2 GO/NO GO Decision :x
2 f Tracking Task 00
P I LOT
T r a j e c t o r y Update Blood Pressure
S u i t I n t e g r i t y Check
0 High R a t e Check 1 2
. t g e C o r r e l a t i o n 1 Report
Oral Temp Blood Pressure
- l l c - GT- 3
SUMMARY FLIGHT PLAN ! COMMAND P I LOT U
E -
Tracking Task
Control S/C t o oO, o O , 0' Oral Temp
Landing Area-Conditions Update ~O-ORDIT 3 Blood Pressure
;o 1 Platform S t a b i l i z a t i o n Check
- 3- 30 Backup C 0 2 Sensor Check
b 3
3 Sea Urchin Egg Exp - Once io P r e r e t r o Checkl i s t
4 10
6 b Align Platform
E T r a n s l a t i o n No. 2
Align Platform 6 10
TR-5 Checkl i s t 1 0
P I LOT
SEC Coolant Pump, B Check PRI Coolant Pump B Check
T r a j e c t o r y Update Tape Plybk
T Contro l Mode C h a r a c t e r i s t i c s Check 1. Control S/C t o Oo, 180°, 0'
P r e r e t r o Checkl i s t
T r a j e c t o r y Update i f requi red
Update f o r T r a n s l a t i o n No. 2 i f r e q u i r e d
- l l d -
GT- 3 SUMMARY FLIGHT PLAN
COMMAND P I LOT
TR-30 Checklist Retrofire bo €k&mtro Checkliet
BBO
- ORBIT 4
EBO
1 OK-
L 00
P I LOT
Reentry Commdnications Exp
- 12 - Crew safety i s
of hours of design,
paramount. Gemini represents thousands
modification, fabrication, inspection,
testing and training.
to crew safety has a redundant (back-up) feature.
Every component or system critical
Launch
The malfunction detection system (MDS) in the launch
vehicle is the heart of crew safety during the powered phase
of flight -- lift off to second stage shut down.
This system was designed for the Gemini launch vehicle
and had no counterpart in the Titan weapon system. Its
f’unction is to monitor Gemini launch vehicle pulbsystem perform-
ance and warn the crew of a potentially catastrophic malfunction
in time for escape, if necessary. The MDS monitors engine
thrust for both stages, turning rates, propellant tank
pressures, staging, Stage I hydraulic pressure, a spacecraft
switchover command or engine hardover.
During the powered phase of flight there are three modes
for crew escape. These are (1) ejection seats, (2) firing the
retrorockets to separate the spacecraft from the launch vehicle,
then initiating the spacecraft recovery system, (3) normal spacecraft separation followed by use of the thrusters and
retroroclqets. For malf’unctions dictating retro-abort node
which occur between 15,000 and 70,000 feet, the astronauts
will not initiate abort until aerodynamic pressure has decreased
to the,point where successflrl separation of the spacecraft from the launch vehicle is assured., more ~
Escape procedures w i l l be i n i t i a t e d by the command
p i l o t following two va l id cues t h a t a malfunction has
occurred. The p a r t i c u l a r malfunction and the time a t which
i t occurs w i l l determine abor t procedures as follows:
1. Li f t -o f f to 15,000 f e e t -- Immediate e , ject ion for all
malfunctions . 2. 15,000 t o 70,000 f e e t -- Delayed r e t ro -abor t for
a l l malfunctions . T h i s ac t ion cons i s t s of arming abort c i r c u i t s , wa i t ing
u n t i l aerodynamic pressure has decreased, then salvo f i r i n s
the four r e t ro rocke t s to separa te from the launch vehicle .
T h i s delay r equ i r e s approximately i'ive seconds.
3. After t he launch vehicle i s above 70,GGO feet,
aerodynamic drag w i l l have decreased to the point where no
delay between engine shutdown and re t ro-abor t i s required Tor
successfu l separat ion. Retro-abort w i l l be used u n t i l a
ve loc i ty o f approximately 20,700 f t / sec (14,100 mph) i s
achieved. For rapid malfunctions, r e t ro -abor t will be i n i t i a t e d
immediately a f t e r r e c e i p t of two v a l i d cues.
malfunctions, re t ro-abor t w i l l be i n i t i a t e d a t the next occurring
fixed t i m e i n order to land near pre-posit ioned recovery vessels .
For s low
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4. For velocities exceeding 20,700 ft/sec, but less
than orbital velocity minus 300 ft/sec, the normal spacecraft
separation abort sequence isused for all malfunctions.
The most probable cause of abort at this time would be'early
shutdown of the booster due to h e 1 depletion. Also, abort
may be requested by ground monitors if the trajectory exceeds
acceptable limits. The general abort plan in this flight
regime is to separate from the launch vehicle, assume retro-
attitude, insert landing area parameters in the spacecraft
computer, retrofire, and descend to a planned recovery area.
In-Flight
There are no single point failures which would jeopardize
crew safety during in-flight operations. A l l systems and
subsystems have redundant features or there is an alternate
mode . The Environmental Control System (ECS) controls suit and
cabin atmosphere, crew and spacecraft equipment temperatures
and provides drinking water and a means of disposing of waste
water.
The spacesuit itself is a redundant system. Should cabin
pressure fail, the spacesuit provides life support.
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- 15 - It i s a f u l l pressure s u i t which works i n conjunction
wi th the ECS. Gaseous oxygen i s d i s t r i b u t e d through the su i t
v e n t i l a t i o n system f o r cooling and r e s p i r a t i o n and provis ions
allow the a s t ronau t t o take i n dr inking water while i n a hard
s u i t (pressur ized) condition.
A 100 percent oxygen environment a t 5.0 psia i n a
pressurized cabin o r 3.7 p s i a i n an unpressurized cabin i s
provided i n spacesui t by the ECS.
ava i l ab le from tanks i n the r een t ry module i n case of emergency
and f o r use during reent ry .
Additional oxygen i s
I n event the f l i g h t must be terminated before mission
completion, the Gemini propulsion systems w i l l permit a
cont ro l led landing i n a contingency recovery area.
Reentry, Landing and Recovery
The Reentry Control System (RCS) con t ro l s the spacecraf t
a t t i t u d e during r e t ro rocke t f i r i n g and reentry. Two complete
and independent systems provide 100 percent redundancy. The
four r e t ro rocke t s a r e wired wi th dua l i g n i t e r s .
The O r b i t A t t i t ude and Maneuver System (OAMS) serves as
a redundant s a f e t y f ea tu re should t h e r e t ro rocke t s f a i l t o
f i r e , &$ case of r e t r o r o c k e t f a i l u r e the OAMS w i l l have been
used t o lower the o r b i t t o the po in t where g r a v i t y and atmos-
drag would cause spacecraf t reent ry .
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- 16 - The OAMS is normally used to perform translation
maneuvers along three axes of the spacecraft and provide
attitude control during orbital phases of the mission.
In GT-3, should the retrorockets fail, reentry will occur
near Ascension Island in the South Atlantic.
Parachutes are used for descent following spacecraft
reentry. The crew has an excellent view of parachute
deplpyment through the Spacecraft windows. If there is a
parachute malfunction the crew will eject themselves from the
spacecraft and use their personal chutes for landing.
Survival equipment is carried on the backs of the ejection
seats and remains attached to the astronauts until they land.
Recovery forces will be provided by the military services
and during mission time will be under the operational control
of the Department of Defense Manager for Manned Space Flight
Support Operations.
Planned and contingency landing areas have been established.
Planned areas are those where the probability of landing is
sufficiently high
forces for support and recovery of crew and spacecraft within
given access times.
to justify pre-positioning of recovery
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Contingency areas a r e a l l o the r areas along the ground
t r a c k where the spacecraf t could p o s s i b v land, The p r o b a b i l i t y
of landing i n a contingency area i s s u f f i c i e n t l y low that
snecial search and rescue techniques w i l l provide adequate
recovery support ,
There a r e four types of planned landing areas:
1, Primary Landing Area -- Landing w i l l occur w i t h
normal terminat ion of the mission a f te r three o rb i t s .
This a rea i s i n the At l an t i c Ocean, o f f Grand Turk Island i n
t h e West Indles , approximately 805 miles southeast of Cape
Kennedy . 2. Secondary Landing Areas -- i n A t l a n t i c Ocean where
a landing would occur i f it i s d e s i r a b l e t o terminate the
mission a f t e r the f i r s t o r second o r b i t f o r any cause, Ships
and a i r c r a f t w i l l be s t a t ioned t o provide support , A i r c r a f t
w i l l be ab le t o drop pararescue personnel and f l o t a t i o n
equipment within one hour a f t e r spacecraf t landing.
3 , Launch Abort Landing Areas -- Along the launch ground
t r a c k between Flor ida and Afr ica where landings would occur
following a b o r t s above 45,000 fee t and before o r b i t a l in-
s e r t i o n .
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- 18 -
Surface sh ips with medical personnel and r e t r i e v a l
equipment, and search and rescue a i rp l anes w i t h pararescue
personnel, f l o t a t i o n equipment and e l e c t r o n i c search c a p a b i l i t y
w i l l be s t a t ioned i n t h i s a r e a before launch.
f u l i n s e r t i o n o f t h e spacecraf t i n t o o r b i t , some o f the sh ips
and planes w i l l deploy t o secondary areas to provide support
on a l a t e r o r b i t , and the remainder w i l l r e t u r n t o home
s t a ti ons .
After t he success-
4 , Launch S i t e Landing Area -- Landing w i l l occur
following an abort during countdown, launch and e a r l y
powered f l i g h t i n which e j e c t i o n seats are used.
an a r e a of approximately 26 m i l e s seaward and th ree m i l e s
toward the Banana River from Pad 19.
o r i en ted along the launch azimuth.
It includes
I t s major axis i s
A spec ia l ized recovery force of land vehicles , amphibious
c r a f t , sh ips and boats, a i rp l anes and he l i cop te r s w i l l be
s t a t ioned i n t h i s area from the t i m e the a s t ronau t s e n t e r t h e
spacec ra f t u n t i l l i f t - o f f plus f i v e minutes.
Recovery access time v a r i e s from 0 minutes f o r a water
landing t o 10 minutes f o r a land landing.
w i l l be taken t o the Pa t r i ck A i r Force Base h o s p i t a l f o r
examinations a f t e r pickup.
The as t ronau t s
c
- more -
- 19 -
Contingency Landing Areas:
Search and rescue a i r c r a f t equipped with e l e c t r o n i c
search equipment, pararescue men and f l o t a t i o n equipment
w i l l be staged along the ground and sea t r a c k so that the
spacecraf t w i l l be located and a s s i s t a n c e given t o the
a s t ronau t s within 18 hours a f te r the recovery fo rces a r e
n o t i f i e d of the probable landing pos i t ion .
- more -
NASA-S-65-2333
ABORT MODES
SEPARATION USING MANEUVER ENGINES TOUCHDOWN CONTROL THRU USE OF:
1) OAMS 2) RETROGRADE ROCKETS 3 ) LIFT MODULATION RETROGRADE ADAPTER
T V / V R 0.8 A
I
I-' \o P,
I
REENTRY MODULE TITAN THRUST TERMINATED PRIOR TO SEPARATION
MODE 11 IM ED1 ATE SEPARATION
DROGUE DEPLOYMENT
DEPLOYMENT (01 :40) ALTITUDE
SPACECRAFT LANDING SEQUENCE -DROGUE CHUTE DEPLOY AT 50,000 FT.
PILOT CHUTE DEPLOY AT 10,600 FT.
R E N D E Z V O U S & RECOVERY SECTION SEPARATION
MAIN CHUTE DEPLOY (REEFED) /-
I
Q 1 SPACECRAFT AT SINGLE POINT SUSPENSION
f
SPACECRAFT IN L A N D I N G POSITION - FIGURE 2.9-2 2-16-65
- 20 -
Manned Space F l i g h t Tracking Network
Within weeks a f t e r the l as t manned Mercury mission
(MA-9) i n May 1963, work began on the $56-million program t o
reshape the network for Gemini's needs. Tracking network
requirements for Gemini missions were q u i t e d i f f e r e n t f rom
and more demanding than those for Mercury.
Mercury flew one man i n one capsule, the network was
b u i l t with e x i s t i n g or "of f - the-she l f" equipment and the
spacecraf t t r a v e l l e d i n a f ixed o r b i t a l path.
Gemini involves n o t only a two-man capsule but, on
rendezvous missions, an Agena t a r g e t vehicle; imposing a
dua l t racking requirement on the s t a t i o n s .
a s t ronau t s w i l l be ab le t o exerc ise considerable con t ro l over
t h e i r o r b i t a l path and w i l l , i n long dura t ion missions, subjec t
a i rborne and ground systems to tremendous r e l i a b i l i t y s t r a i n s .
I n terms of information t o be handled the gear used i n t h e
Gemini network w i l l be asked t o absorb some 40 times the amount
generated by Mercury.
items alone are th ree times those of Mercury.
Moreover, Gemini
Gemini capsule measurements o f 275 te lemetry
An indus t ry team (comprised of ITT, Canoga, Bendix, E lec t ro-
Mechanical Research, RCA, IBM, AT&T, Col l ins Radio, Radiation, Inc.,
and UNIVAC) helped put the Gemini n e t ''on l i ne . "
o f 1964 the equipments were i n s t a l l e d , s t a t i o n staffs were t r a ined
and up t o s t r eng th and the network was exercised by the Saturn I SA-6, GT-1, and Centaur AC-3 missions.
By the spr ing
- more -
- 21 -
Some new equipment has been installed, some old equipment
modified, a few stations have been dropped from the network,
a few added. The most basic change in the network is its
language.
system to acquire a data handling capability, a speed and
precision which has already out-distanced Mercury's best.
It has changed from an analog system to a digital
The Manned Space Flight Network f o r Gemini is composed
of tracking and data acquisition facilities around the world,
a Mission Control Center at Cape Kennedy and a computing and
communications center at Goddard Space Flight Center, Green-
belt, Md.
when completed, will be used for many of the flight control
and computing functions presently performed at'dze Mission
Control Center, Cape Kennedy, and Goddard Space Flight
Center )
(The Mission Control Center at Houston, Tex.,
The basic network consists of seven primary land sites;
two ships, the Rose Knot Victory and Coastal Sentry Quebec;
six additional land stations; and the computing/comnications
and c o n t r o l centers.
- more -
- 22 -
The loca t ions of t he land s t a t i o n s a r e as follows:
Primary S ta t ions
Cape Kennedy, F l a , , and down-
range A i r Force Eastern T e s t
Range s i t e s .
Bermuda
Grand Canary I s l and
"Carnarvon, Australia
Hawaii
Additional S t a t ions
Kano, Nigeria
*Madagascar (Tananarive)
Canton Is land
Point Arguello, Calif.
White Sands, N , M.
Egl in AFB, Fla .
Guaymas, Mexico
Corpus Chris t i , Tex.
Two Ships:. The Rose Knot
and Coastal Sentry
Other t racking and data a c q u i s i t i o n f a c i l i t i e s , such
as r e l a y a i r c r a f t , ins t rumentat ion sh ips , communications, r e l a y
s t a t i o n s , e t c . , w i l l be ca l l ed up as required and in t eg ra t ed
i n t o the bas i c Network. Also considered part of the network
i s the Network Engineering and Training Center a t Wallops
I s l and , Vi rg in ia .
* The s t a t i o n a t Muchea, Aus t ra l ia , has been deac t iva ted as a r e s u l t of t he new s t a t i o n a t Carnarvon. Also the Zanzibar s t a t i o n was removed and Tananarive, a STADAN s t a t i o n , i s supporting i n its place.
- more -
- 23 -
Network Responsibility
Manned Spacecraft Center (MSC). The MSC has the overall
management resbonsibility of the Gemini program.
and mission control of the Network immediately preceding and
during a mission simulation or an actual mission is the
responsibility of the MSC.
The direction
Goddard Space Flight Center (GSFC). NASA has centralized
the responsibility for the planning, implementation, and
technical operations of manned space flight tracking and
data acquisition at the Goddard Space Flight Center.
the GSFC has the responsibility for the technical operation
of the Network f o r Gemini. Technical operation is defined as
the operation, maintenance, modification, and augmentation of
tracking and data acquisition facilities to function as an
instrumentation network in response to mission requirements.
About 370 persons directly support the network at Goddard.
Hence,
Weapons Research Establishment(WRE). The WRE, Department
of Supply, Commonwealth of Australia, is responsible f o r the
maintenance and operation of the Network stations in Australia.
Contractual arrangements and agreements define this cooperative
effort.
- more -
- 24 - Department of Defense (DOD). The DOD i s responsible
f o r the maintenance and ape ra t iona l c o n t r o l of those DOD
a s s e t s and f a c i l i t i e s required t o support P ro jec t Gemini.
These include network s t a t i o n s a t the Eastern T e s t Range,
Western Test Range, and the A i r Proving Ground Center,
NASCOM. The e n t i r e network i s supported by the NASA
Communications Network. This Division, a Goddard r e s p o n s i b i l i t y ,
i s respons ib le f o r the establ ishment and operat ion of the
world-wide ground communications network that provides
t d k t h e
c o n t r o l cen te r s f o r t he network.
voice, and data l i n k s between the s t a t i o n s and
It links 89 s t a t i o n s , including 34 overseas poin ts , with
message, voice and data communications. I t s c i r c u i t s and
te rmina ls span 100,000 route miles and 5OO,OOO c i r c u i t miles.
Also part of NASCOM i s the voice communication ne t .
A soph i s t i ca t ed switchboard system, with mul t ip le dual-
opera t ing consoles, enables one opera tor t o devote f’ull
a t t e n t i o n t o any s p e c i a l mission conferences, This system i s
c a l l e d SCAMA I1 ( S t a t i o n Conferencing and Monitoring
Arrangemeqt).
u l t i m a t e l y be expanded t o handle 220 l i n e s .
to-point connections and conference arrangements are poss ib le .
SCAMA I1 can now handle 100 l i n e s and can
Both poin t -
A l l l i n e s can be connected i n t o one conference without loss of
q u a l i t y . The S C m o p e r a t o r can add conferees o r remove them. He a l s o control3 which of the conferees can talk filch cm Tis t en only. - more -
- 25 -
The SCAMA cur ren t ly has 10 times the c a p a b i l i t y of the
network used f o r Mercury.
One of the most c r i t i c a l funct ions the world-wide network
must perform i s tha t of obtaining data and making high-speed
near-real-t ime computations. During a f l i g h t , the t racking
data from the Manned Space F l i g h t Network s t a t i o n s a r e sent
v i a ground communications to the Goddard Space F l igh t Center,
f o r processing. The development o f an extensive computer
program was required t o handle the t racking data and t o
make c r i t i c a l computations f o r the so-called "go or no-go"
and r e t r o f i r e and r een t ry decis ion within mil l iseconds of
t racking measurements. A t the Goddard Computing Center, th ree
IBM 7094 computers a re i n s t a l l e d . Two operate i n p a r a l l e l
t o accept pos i t i on data i n d i g i t a l form d i r e c t l y from the
s t a t i o n s and perform computations for each of the separa te
f l i g h t phases: the launch phase, the o r b i t a l phase, and
the recovery phase. The o the r serves as a backup,
The Computing Center a l s o houses various d isp lays and
p l o t board presenta t ions for v i s u a l i nd ica t ion o f capsule
loca t ion , ve loc i ty , and s ta tus of c e r t a i n c r i t i c a l capsule
systems.
The number o f people a t Goddard, a t t he s t a t i o n s and a t
o the r support
depot , t o t a l s some 1500 personnel f o r the e n t i r e network.
groups such as the t r a i n i n g cen te r and a l o g i s t i c s
- m o r e -
- 25 -
Voice Communications
Remote Air to Ground Voice Communications
Air to Ground Voice Communications
F1 ight Controller Manned
High Speed Radar Data
X XXI X
x x
Telemetry Communica- tions
RF Command
Down Range Up Link
X x x x x
x x
X X
X X
x
X
Digital Command System X X
Gemini Launch Vehicle Command
On Site Data Processor (1218)
Telemetry Real Time Display
- X X
X X x
x x 1 x Telemetry Receiver & Recorder
Acquisition Aid
X x x
x x - x x
x x X X X I x x
C-Band Radar I ~
X X
I
- 26 -
EXPERIMENTS
NASA has scheduled a series of scientific, biological
and technological experiments for Project Gemini. These
were first undertaken in Project Mercury and involve
experiments submitted by NASA, the Department of Defense and
the scientific community.
Reentry Communications
An object reentering the Earth's atmosphere from space
generates extremely high temperatures. These temperatures
ionize the air and create a plasma sheath which surrounds
the object and effectively eliminates radio communications with
it. Project Mercury manned space flights suffered l o s s of
telemetry and voice communications during reentry.
Research has developed a method for restoring radio
communications during this period. It has been determined
that injecting fluid into the Lonized plasma will decrease
the amount of ionization to a level where communications are
possible. The technique has been successful for objects with
a maximum nose diameter of eight inches and at velocities up
to approximately 18,000 feet per second (12,270 mph). This
experiment is designed to establish whether the same technique
can be applied to a large, blunt, high-velocity vehicle. The
experiment was designed by the NASA Langley Research Center,
Hampton, Va. and I s sponsored by the NASA Office of Advanced Research and Technology. There are three experimenters, The0
Sims, W.F. Cuddihy, and L. C. Schroeder, all of Langley. - more -
- 27 -
The GT-3 f l i g h t o f f e r s an opportunity f o r an engineering
experiment under very p r a c t i c a l condi t ions.
During the Gemini reent ry , water w i l l be in j ec t ed
i n extremely br ief , timed pulses a t d i f f e r e n t flow rates
i n t o the ionized plasma sheath. S igna l l e v e l s received
w i l l be monitored and recorded f o r use i n eva lua t ing the
e f f ec t iveness of the d i f f e r e n t flow rates. For purposes
of the experiment, te lemetry s i g n a l measurements w i l l be
s u f f i c i e n t , and the re w i l l be no attempt t o r e s t o r e as t ronaut
voice channel communications on t h i s f l i g h t .
The experiment c o n s i s t s of a water expulsion system
designed t o f i t on the in s ide sur face of the spacec ra f t ' s
r i g h t main landing gear door. The system i s completely s e l f -
contained except for the experiment a c t i v a t i o n switch i n s i d e
t h e cabin. Tota l weight of the equipment serviced f o r f l i g h t
i s approximately 85 pounds.
A s t he spacecraf t r e e n t e r s the Earth 's atmosphere,
the communications blackout w i l l begin a t approximately
3OO,OOO f e e t . A t a spec i f i ed time a f t e r r e t r o - f i r e the
p i l o t (John Young) w i l l f l i c k a switch t o start the experiment.
- more -
- 28 -
The switch w i l l open a solenoid shut-off valve and
a l l o w ni t rogen gas pressur iza t ion of the water s torage tank.
It w i l l a l s o s tar t the mechanically run i n J e c t i o n sequence
t imer. This w i l l a c t i v a t e the i n j e c t i o n nozzle solenoid
valves a t t h e i r programmed times t o allow i n j e c t i o n of' viater
i n t o the spacecraf t flow f i e l d . The water supply w i l l be
exhausted i n approximately 150 seconds.
E f fec t s of Zero Gravity on the Growth of Sea Urchin 3ggs
This experiment i s designed t o explore the p o s s i b i l i t y
of the exis tence o f a g r a v i t a t i o n a l f i e l d e f f e c t on c e l l a
exposed to low g rav i ty condi t ions. Ce l lu l a r e f f e c t s are
more e a s i l y de tec tab le i n simple c e l l systems, and t h i s
experiment w i l l i nves t iga t e zero-gravity e f f e c t s on sea
urchin eggs during s e n s i t i v e stages o f development, such a s
f e r t i l i z a t i o n and c e l l d iv is ion . For comparison, a s f x i l a r
s e r i e s of cont ro l samples w i l l be developed simultaneously a t
the launch s i t e .
The experiment cons i s t s of a metal cy l inder containing
e i g h t separa te samples o f sea urchin eggs, sperm, and a
f i x a t i v e so lu t ion . The capsule i s mounted in s ide the cabin
on the l e f t hatch.
- more -
- 29 -
A t designated times, the eggs and the sperm w i l l be
uni ted t o s t a r t t he f e r t i l i z a t i o n and growth process. After
a spec i f i ed time, the f i x a t i v e so lu t ion w i l l be appl ied t o
t he egg embryo t o s t o p i t s growth. Rotation of a handle a t
one end o f the cy l inder a c t i v a t e s e i t h e r the f e r t i l i z a t i o n
o r the f i x a t i o n process. The a c t u a l sequence i s prearranged
by cy l inder design.
The cy l inder i s 3 1/4 inches i n diameter and 6 3/4
inches long. It weighs 25.4 ounces.
The experiflent w i l l , be conducted by the NASA Ames
Research Center. Dr. Richard S. Young of tha t Center i s the
experimenter. The sponsor i s the NASA Office of Space
Sciences.
Syne rg i s t i c E f fec t of Zero Gravity and Radiation on White Blood Cells
This experiment w i l l be conducted by the Atomic Energy
Commission and i s sponsored by the NASA Off ice of Space
Sciences. Dr. Michael Bender of Oak Ridge National Laboratory
i s the experimenter.
The objec t ive i s t o examine the b i o l o g i c a l e f f e c t s of
r ad ia t ion . This i s important because of poss ib le r a d i a t i o n
exposure during prolonged f l i g h t s . The experiment w i l l t e s t
the p o s s i b i l i t y that weightlessness i n t e r a c t s with r a d i a t i o n
t o produce unpredicted e f f e c t s g r e a t e r than the sum of t h e i r
i n d i v i d u a l e f f e c t s - more -
- 30 -
The experiment w i l l measure the changes i n human blood
samples exposed t o a known quant i ty and q u a l i t y o f r a d i a t i o n
during the zero g rav i ty phase of the mission. For comparison,
a similar s e r i e s of con t ro l samples w i l l be exposed
simultaneously a t the launch s i t e . An ana lys i s a l s o w i l l be
made on blood samples taken from the f l i g h t crew immediately
before and a f t e r the mission.
The r a d i a t i o n source w i l l be Phosphorus-32 an isotope
which emits only a s ing le beta . p a r t i c l e wl th an average
energy of 0.7 mev (mi l l ion e l ec t ron v o l t s ) .
The experiment i s housed i n a hermetical ly sealed
aluminum box 3.7 inches wide, 1.3 inches deep, 3.8 inches
long. It weighs approximately one pound and i s located on
the r i g h t hatch in s ide the cabin.
I r r a d i a t i o n of the b lood samples i s i n i t i a t e d manually
by tw i s t ing a handle on the box.
Cardiovascular E f f e c t s o f Space F l i g h t
T h i s i s a cont inuat ion of s t u d i e s begun during P r o j e c t
Mercury t o evaluate the e f f e c t s o f prolonged weightlessness
on the cardiovascular system. Astronauts Sch i r r a and Cooper
experienced lower than normal blood pressure i n the e r e c t
pos i t i on immediately a f te r emerging from the spacecraf t .
- more -
- 31 - The experiment will be conducted by the Space Medicine
Branch of the Crew Systems Division of the Manned Spacecraft
Center and is sponsored by the NASA Office of Manned Space
Flight.
Comparisons will be made of the astronauts' preflight
and postflight blood pressures, blood volumes, pulse rates,
and electrocardiograms. The data will reveal the cardiovascular
and blood volume changes due to heat stress, the effect of
prolonged confinement, dehydration, fatigue, and possible
effects of weightlessness. There are no inf'light requirements.
Measurements will be taken before, during, and after a
head-up tilt of 80 degrees from the horizontal.
The astronauts will remain in the spacecraft while it
is hoisted aboard the recovery vessel.
recorder w i l l be attached to each astronaut before he leaves
the spacecraft, and 61ood pressure and electrocardiogram
measurements will be taken. Each astronaut will then egress
from the spacecraft and stand on the vessel's deck. Blood
pressure and ECG measurements will be recorded automatically
before, during, and for a short time after egress. The
astronauts will then go to the shipls medical facility for
the tilt table tests.
A portable biomedical
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- 32 -
MEDICAL CHECKS
Medical checks w i l l be based on biomedical te lemetry and
voice communications. T h i s data w i l l be used t o evaluate
genera l condi t ion of the crew, blood pressure, and o r a l
temperature . PHOTOGRAPHY
A 7Omm Hasselblad still camera and a 16m motion
p i c t u r e camera w i l l be ava i l ab le f o r genera l purpose
photography.
FOOD ETVALUATION
Evaluation o f f l i g h t food packaging and handling i s
one of the tasks scheduled during the mission. One hour
during the second o r b i t has been provided i n the p i l o t ' s
f l i g h t plan t o v e r i f y food items f o r use i n l a te r Gemini
missions.
Two meals of four items each w i l l be aboard the
spacecraf t . Each meal w i l l be contained i n an aluminum f o i l
laminated over-wrap. There w i l l be two rehydrated items and
two b i t e - s i z e i tems t o a meal, sugar less chewing gum, and
a wet pack f o r c leansing hands and face.
The food w i l l be stowed i n a box on the l e f t s ide of the
Gemini cockpi t . During the second o r b i t , the command p i l o t
w i l l t r a n s f e r t he meals t o the p i l o t i n the r i g h t seat who w i l l eva lua te each i t e m . - more -
- 33 - The rehydrated i t e m s w i l l be r econs t i t u t ed by adding
water wi th a s p e c i a l water gun developed by Manned Spacecraft
center engineers. When the gun i s i n s e r t e d i n t o the nozzle
on the food conta iners i t can t r a n s f e r water i n t o the food
without s p i l l i n g . The b i t e s i z e items do not need water.
They a r e coated t o prevent crumbling. For c u t t i n g
open the overwrap, and packaging around b i t s i z e items, the
a s t ronau t has a s p e c i a l p a i r of s c i s s o r s , stowed i n a
pocket on the l e f t l eg of h i s s u i t .
After the p i l o t has r econs t i t u t ed the food and sampled
it, he w i l l go through the food wasted.sposa1 procedure. I n
each package of the freeze-dr ied food, t h e r e i s a yellow
t a b l e t o f food d i s i n f e c t a n t i n a separate pouch. When it i s
placed i n the food pouch, it a c t s chemically t o prevent
spoi lage of the remaining food.
All products used during the f l i g h t must conform with
s t r i n g e n t b a c t e r i o l o g i c a l requirements which a r e higher than
normal indus t ry requirements on commercially processed food.
The food formulation concept was developed by the U.S.
Army Laboratories, Natick, Wss. Overal l food procurement,
processing, and packaging w a s performed by the Whirlpool
Corp., S t . Joseph, Mich. P r i n c i p a l food subcontractors are
S w i f t and Co., Chicago, and P i l l s b u r y Co., Minneapolis.
- more -
- 34 -
Meal A
Beef P o t Roast -- Freeze d r i ed beef cubes i n gravy.
The i tem i s i n bar shape and weighs 27 grams. Formulated
from a r ec ipe of cooked diced beef, beef j u i c e s and water.
Orange Ju ice -- Contains 20.7 grams of orange juice
c r y s t a l s and 0.3 grams o f orange o i l granules. An i n s t a n t
product.
Meal B
Applesauce -- Commercially prepared i n s t a n t powder.
Weighs 42 grams and contains mixture of i n s t a n t applesauGe
and i n s t a n t apple ju ice .
Grapefrui t Juice -- Commercially prepared i n s t a n t
powder. Weighs 2 1 grams.
Brownies -- Compressed irito cubes with no s p e c i a l drying
procedure.
Contents include shortening, b i t t e r chocolate, genera l purpose
Has double coat ing o f s t a r c h and g e l a t i n .
f l o u r , chemical leavening, salt , whole f r e s h eggs, granulated
sugar, v a n i l l a f lavoring, and midget pecans. Tota l weight
o f six cubes i s 45 grams.
Chicken b i t s -- Six pieces, f reeze dr ied . Tota l weight
i s 24 grams. Contains diced chicken., water, gravy m i x ,
shortening, and minced onion.
- more -
- 35 -
G E M I N I SURVIVAL PACKAGE
The Gemini su rv iva l package contains 14 i tems designed
t o support an a s t ronau t i f he should land outs ide normal
recovery a reas .
The package weighs 23 lbs . and has two sec t ions . One
sec t ion , holding a 3 1/2-pound water container and machete
i s mounted by the a s t r o n a u t ' s l e f t shoulder. The main
package, containing the l i f e ra f t and r e l a t e d equipment, i s
mounted on the back of the e j e c t i o n s e a t . Both packages
a r e a t tached t o the a s t r o n a u t ' s personal parachute harness
by a nylon l i ne . After e j e c t i o n from the spacecraf t , as
the s e a t fa l l s c l e a r and the parachute deploys, t he su rv iva l
k i t w i l l hang on a l i n e , ready f o r use as soon as the a s t ronau t
lands.
In f l a t ed , the one-man l i f e ra f t i s f i v e and one half
ft. long and th ree f t . wide. A C02 b o t t l e i s a t tached for
i n f l a t i o n . The r a f t i s a l s o equipped with a sea anchor, sea
dye markers, and a sun bonnet of nylon ma te r i a l with an
aluminized coat ing which the a s t ronau t can place over h i s
head.
- more -
- 36 -
I n h i s su rv iva l k i t , the as t ronaut a l s o has a r ad io
beacon, a combination su rv iva l l i g h t , sunglasses, a medical
k i t , and a d e s a l t e r k i t assembly. The combination su rv iva l
l i g h t i s a new developmentfbr the Gemini k i t , combining many
indiv idua l items which were ca r r i ed i n the Mercury k i t .
About the s i z e o f a paperback novel, the CSL contains
a s t robe l i g h t for s igna l ing a t night , a f l a s h l i g h t , and a
s i g n a l mirror b u i l t i n on the end of the case. It a l s o
contains a small compass.
There a r e th ree c y l i n d r i c a l ca r t r idges in s ide the case.
Two contain b a t t e r i e s for the l i g h t s . The t h i r d contains a
sewing k i t , 14 f e e t o f nylon l i n e , cot ton ba l l s and a
s t r i k e r f o r kindl ing a f i r e , halazone t a b l e t s for water
p u r i f i c a t i o n , and a whis t le ,
The d e s a l t e r k i t includes e i g h t d e s a l t e r b r i c k e t t e s ,
and a processing bag. Each b r i c k e t t e can d e s a l t one p i n t o f
seawater . The medical k i t contains a one cubic centimeter i n j e c t o r
f o r pain, and a two cubic centimeter i n j e c t o r f o r motion
sickness. There also a r e s t imulant , pain, motion sickness,
and a n t i b i o t i c t a b l e t s and a s p i r i n .
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- 37 -
The water container was manufactured a t Manned
Spacecraf t Center by members of the Crew Systems Division.
Other i tems were provided by the following contractors :
machete, Case Knife Co., Bradford, Pa. ; r a d i o beacon, Sperry
Co., Phoenix, Ariz.; sunglasses, Cool Ray Co., Houston, Tex.;
combination su rv iva l l i gh t , ACR Elec t ronics , New York City;
medical k i t i n j e c t o r s , Rodona Research Corp., Bethesda, Md.;
d e s a l t e r k i t assembly, Department of Defense; l i f e raft,
S t e i n t h a l Co., New York City; C02 container , Arde Corp.,
Paramus, N. J .
GEMINI SPACECRAFT
The Gemini spacecraf t i s conica l shaped and c o n s i s t s
of two major assemblies, the r een t ry module and adapter
sec t ion . It i s 18 feet , 5 inches i n length and 10 fee t
ac ross a t the base.
The r e e n t r y module i s separated i n t o th ree primary
sec t ions : (1) Rendezvous and recovery sec t ion (R&R). ( 2 )
Reentry c o n t r o l s ec t ion (RCS); (3) Cabin sec t ion .
The R&R sec t ion i s the forward sec t ion of the spacecraf t
and i s a t tached t o the RCS sec t ion . Radar equipment i s not
c a r r i e d f o r t h i s f l i g h t . Housed i n t h i s s ec t ion a r e the
drogue, p i l o t and main parachutes.
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The RCS sec t ion , located between, and mated t o , the
R&R and cabin sec t ions o f the spacecraf t . It contains the
f u e l and oxid izer tanks, valves, tube assemblies and t h r u s t
chamber assemblies ( T C A ) . A parachute adapter assembly i s
on the forward face for main parachute attachment.
The cabin sec t ion houses the crew. It i s located between
the RCS and adapter sec t ions . It w i l l provide proper water
f l o t a t i o n a t t i t u d e . The shape also allows space between i t
and the outer conica l shell for i n s t a l l a t i o n of equipment.
The outer s h e l l i s covered wi th Reng 4 1 sh ingles with an
a b l a t i v e hea t s h i e l f on the blunt end ?or heat protec t ion .
The adapter cons i s t s o f a re t rograde sec t ion and a n
equipment sec t ion .
f o r the cooling system a r e contained i n the re t rograde
sec t ion . The equipment s ec t ion holds b a t t e r i e s for e l e c t r i c a l
power, f u e l f o r the o r b i t a l t i t u d e and maneuver system, and
the primary oxygen f o r the environmental con t ro l system.
Retrograde rockets and p a r t o f the rauiator
The equipment s ec t ion also serves as a r a d i a t o r for the
spacec ra f t ' s cooling system which i s contained i n the sec t ion .
The equipment s ec t ion i s j e t t i soned immediately p r i o r
t o r e t r o f i r e , and the retrograde sec t ion i s j e t t i soned a f t e r
r e t r o f i r e .
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- ' 3 9 -
The Gemini spacecraf t provides 50 per cent more cabin
space than the Mercury spacecraf t . Gemini's r een t ry module
i s 11 f e e t high and 7 1/2 f e e t i n diameter a t i t s base, compared
t o nine f e e t high s i x f e e t i n diameter for Mercury.
The Gemini equipment adapter i s 7 1/2 f e e t high and
10 f e e t i n diameter a t i t s base.
Launch weight of the spacecraf t i s approximately 7,000
pounds. Landing weight of the r een t ry module i s about
4,700 pounds.
P r inc ipa l s t r u c t u r a l materials i n the r een t ry module
are t i tanium, with Rene' 4 1 and beryll ium used f o r shingles .
The adapter i s constructed mainly of magnesium.
Prime cont rac tor f o r the Gemini spacecraf t i s McDonnell
A i r c r a f t Corp., S t . Louis.
GEMINI LAUNCH VEHICLE
The Gemini Launch Vehicle i s a modified T i t * I1 cons is t ing
of two stages.
Stage I i s 63 f e e t high, and s tage I1 i s 27 f e e t high.
Diameter i s 10 feet . Overal l length of'the launch vehic le
including the spacecraf t i s 109 feet .
Launch weight, including the spacecraf t i s about 340,000
pounds.
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PROPULSION SYSTEMS OAMS, RCS, RETRO LOCATION IN SPACECRAFT
EQUIPMENT SECT10
RnROGRADE SECn
RE-ENTRY SECT1
FIGURE 2.5-1 2- 16-65
Propulsion is provided by two stage I and one stage
I1 liquid propellant engines which burn a 50-50 blend of
monomethyl hydrazine and unsymmetrical-dimethyl hydrazine
as fuel, with nitrogen tetroxide as oxidizer.
Stage I engines produce about 430,000 pounds of thrust
at lift-off, and the stage 11 engine produces about 100,000
pounds of thrust at altitude. Fuels are storable for easy
handling and hypergolic (ignite on contact with each other),
which eliminates the need for an ignition system,
Titan I1 was chosen for Gemini because of its simplified
operation, thrust and availability. The following modifications
were made:
a. b.
C.
d.
e.
f.
Q .
h.
i.
J .
Additions for a malfunction detection system.
Modifications of flight control system.
Modification of electrical system.
Substitution of radio guidance for inertial guidance.
Deletion of retro rockets and vernier bottles.
New stage I1 equipment t russ .
New stage II forward oxidizer skirt assembly. Simplification of trajectory tracking requirements.
Modification of hydraulic system.
Modification of instrumentation system.
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- 41 - GLV program management for NASA is under the direction
of the Space Systems Division of the Air Force Systems
Command. Contractors include: air frame and system
integration, Martin, Baltimore (Md. ) Division; propulsion
systems, Aerojet-General Corp., Sacramento, Calif.; radio
command guidance system, General Electric Co., Syracuse,
N. Y.; ground guidance computer, Burroughs Corp., Paoli, Pa.;
systems engineering and technical direction, Aerospace Corp.,
El Segundo, Calif.
GEMINI SPACE SUIT
The Gemini space suit which will be used on this mission
was designed as a close fitting f 'u l l pressure suit. The
wearer can take off the helmet and gloves in flight. The
remainder of the suit is designed for continuous wear. The
communications system (earphones and microphones) is an integral
part of the suit.
The inner layer of the suit is a rubberized material,
and the outer covering is a nylon material.
Air inlet and outlet connections are located at waist
level. Oxygenis provided from containers stowed in the
spacecraft's adapter section. During reentry, after the
adapter section has been jettisoned, astronauts use an oxygen
supply located in the reentry module. - more -
- 42 -
The gloves a r e a t tached t o the s u i t a t a r o t a t i n g wrist
j o i n t which allows full wrist movement. A small b a t t e r y pack
and ind iv idua l f i n g e r t i p l i g h t s a r e mounted on each glove
90 t h a t the a s t ronau t s can read instruments on the n ight
s i d e o f the Earth while the cabin l i g h t i s o f f .
A pocket i s located on the in s ide of each l eg between
the ankle and knee. The l e f t pocket contains a s p e c i a l
pa i r of s c i s s o r s for opening food packages, and the r i g h t
pocket holds a parachute shroud l i n e c u t t e r . The c u t t e r would
be used a f t e r landing t o prevent the a s t ronau t from becoming
entangled by parachute l i n e s .
The a s t ronau t dons the suit through a zipper opening
which runs from the c ro tch up the e n t i r e back o f t hecsu i t .
The s u i t has been developed by M S C l s Crew Systems
Division. P r i m e con t r ac to r i s the David Clark C o . , Worcester,
Mass . Each a s t ronau t i s provided wi th t h ree s u i t s . One i s
f o r t r a in ing , the second i s worn during the mission, and the
t h i r d i s a back-up.
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CREW BIOGRAPHIES
NAME: V i r g i l I. "Gus" Grissom
BIRTHPLACE AND DATE: Mitchel l , Ind., A p r i l 3, 1926
EDUCATION: Bachelor of Science degree i n mechanical engineering
MARITAL STATUS: Married t o the former B e t t y L. Moore of
CHILDFUN: Sco t t , May 16, 1950; Mark, Dec. 30, 1953.
from Purdue Universi ty
Mitchel l , Ind.
Grissom i s a Major i n the United S t a t e s A i r Force, and
received h i s wings i n March, 1951. He flew 100 combat missions
i n Korea i n F-861s w i t h the 334th F ighter - In te rceptor Squadron.
H e l e f t Korea i n June 1952 and became a je t i n s t r u c t o r a t
Bryan, Tex.
I n August 1955, he entered the A i r Force I n s t i t u t e of
Technology a t Wright-Patterson A i r Force Base, Ohio, t o s t u d y
aeronaut ica l engineering. I n October 1956, he attended t h e
Test P i l o t School a t Edwards A i r Force Base, Calif., and r e -
turned t o Wright-Patterson A i r Force Base i n 1957 as a t e s t
p i l o t assigned t o the f i g h t e r branch.
Grissom has logged more than 4,000 hours f l y i n g time,
including more than 3,000 hours i n j e t a i r c r a f t . H e was
awarded the Distinguished Flying Cross and the A i r Medal w i t h
C lus t e r f o r s e rv i ce i n Korea.
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NAME: John W. Young
BIRTHPLACE AND DATE: San Francisco, C a l i f . , Sept. 24, 1930
EDUCATION: Bachelor of Science degree i n aeronaut ical engineering from Georgia I n s t i t u t e of Technology
MARITAL STATUS: Married t o the former Barbara V. White of Savannah, Ga.
CHILDREN: Sandy, A p r i l 30, 1957; John, Jan. 17, 1959
Upon graduation from Georgia Tech, Young entered the
United States Navy and i s now a Lieutenant Commander i n that
service.
l a t e r program manager of the F4H weapons systems project ,
doing test and evaluat ion f l i g h t s and w r i t i n g t echnica l re-
po r t s .
From 1959 t o 1962 he served as a test p i l o t , and
H e served as maintenance o f f i c e r f o r all-weather Fighter
Squadron 143 a t the Naval A i r Stat ion, N i r a m a r , C a l i f , I n
1962, Young set world time-to-climb records i n the 3,000
meter and 25,000 meter events i n the F4B Navy fighter.
H e has logged more than 3,200 hours f ly ing t i m e , ihclud-
ing more than 2,700 hours i n jet a i r c r a f t .
Young w a s among the group of nine as t ronauts selected by
NASA i n September 1962.
ove ra l l as t ronaut t r a i n i n g program he has had special ized
du t i e s including monitoring development of environment cont ro l
systems and spacecraf t edect ion seats and couches,
In addi t ion t o pa r t i c ipa t ion i n the
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- 46 -
NAME: Walter M. Schi r ra , Jr.
BIRTHPLACE AND DATE: Hackensack, N. J., March 12, 1923
EDUCATION: Graduate of the United S t a t e s Naval Acaday
MARITAL STATUS: Married t o the former Josephine Fraser of S e a t t l e , Wash.
Schirra , a,Navy Commander, received f l i g h t t r a i n i n g a t
Pensacola, Naval A i r S ta t ion .
A s an exchange p i l o t with the United S t a t e s A i r Force,
154th F ighter Bomber Squadron, he flew 90 combat missions i n
F-84E a i r c r a f t i n Korea and downed one M I G with another
probable.
A i r Medals for h i s Korean serv ice .
He received the Distinguished Flying Cross and two
He took p a r t i n the development of the Sidewinder missile
a t t he Naval Ordnance Training Sta t ion , China Lake, Calif.
Sch i r r a was p r o j e c t p i l o t f b r the F7v3 Cutlass and i n s t r u c t o r pilot f o r the Cutlass and t h e J?J3 Fury.
Sch i r r a flew F3H-2N Demons as operat ions o f f i c e r of the 124th
F ighter Squadron onboard the Carrier Lexington i n the Pac i f i c .
He at tended the Naval A i r Safety Offic&School a t the
Univers i ty of Southern Cal i forn ia , and completed t e s t p i l o t
t r a i n i n g a t the Naval A i r Center, Patuxent River, Md. He
was la te r assigned a t Patuzent i n s u i t a b i l i t y development
work on the F4H.
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- 4'( -
He has more than 3,800 hours f l y i n g time, including
more than 2,700 hours i n j e t a i r c r a f t .
Sch i r r a was one o f t he seven Mercury a s t ronau t s named
i n Apr i l 1959.
On Oct. 3, 1962, Sch i r r a flew a s i x - o r b i t mission i n
h i s "Sigma 7" spacecraf t . The f l i g h t l a s t e d nine hours and
13 minutes from l i f t o f f through landing and he a t t a i n e d a
ve loc i ty of 17,557 miles pe r hour, a maximum o r b i t a l a l t i t u d e
of 175 s t a t u t e miles and a t o t a l range of almost 144,000
s t a t u t e miles.
about 275 miles no r theas t of Midway Is land .
The impact lpoint was i n the p a c i f i c Ocean,
He was awarded
the NASA Distinguished Sekvice Medal f o r h i s f l i g h t .
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NAME: Thomas P. S ta f ford
BIRTHPLACE AND DATE: Weatherford, Okla., Sept. 17, 1930
EDUCATION: Bachelor of Science degree from United St&L&e3
MARITAL STATUS: Married t o the former Faye L, Shoemaker o f
CHILDFEN: Dianne, J u l y 2, 1954; Karin, Aug. 28, 1957
Naval Academy
Weatherford, Okla.
Stafford, an A i r Force Major, was commissioned i n the
United S t a t e s A i r Force upon graduation from the U.S. Naval
Academy a t Annapolis. Following h i s f l i g h t t r a in ing , he flew
f i g h t e r i n t e rcep to r a i r c r a f t i n the United S t a t e s and
Gerrhan;r, and l a t e r a t tended the United S t a t e s A i r Force
Experimental F l igh t Test School a t Edwards A i r Force Base,
C a l i f . He served as Chief of the Performance Branch, USAF
Aerospace Research P i l o t School a t Edwards.
he was responsible f o r supervis ion and adminis t ra t ion of the
f l y i n g curriculum f o r s tudent t e s t p i l o t s . He a l s o served
as an i n s t r u c t o r i n both f l i gh t t e s t t r a i n i n g and spec ia l ized
academic subjects .
i n and d i r ec t ed the w r i t i n g of f l i g h t t e s t manuals f o r use
by the staff of s tudents .
I n t h i s assignment
He es tab l i shed bas ic textbooks and pa r t i c ipa t ed
S taf ford i s co-author of the P i l o t * s Handboqk. f o r Performance
F l i g h t Testina; and Aerodynamics Handbook f o r Performance F l i g h t
Testinff. - more -
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- 6i7 -
- 50 -
PROJECT OFFICIALS
George E. Mueller
William C. Schneider
E, E. Christensen
Charles W. Mathews
Christopher C. Kraft
Associate Administrator, Office of Manned Space Flight, NASA Headquarters. Acting Director, Project Gemini . Deputy Director, Project Gemini, Office of \ Manned Space Flight, NASA Headquarters.
Director, Missions Operations, NASA Headquarters
Gemini Program Manager, Manned Spacecraft Center, Houston, Tex.
Mission Director, Manned Spacecraft Center, Houston, Tex .
Lt. Gen. Leighton I. Davis USAF, National Range Division Commander and DOD Manager of Manned Space Flight Support Operations.
Maj. Gen. V. 0. Huston
Col. Richard C. Dineen
Lt, col. John G. Albert
USAF, Deputy DOD Manager
Director, Directorate Gemini Launch Vehicles, Space Systems Division,, Air Force Systems Commdnd.
Chief, Gemini Launch Division, 6555th Aerospace Test Wing, Air Force Missile Test Center, Cape Kennedy, Fla.
USN, Commader Task Force 140.
- end -
- 50a -
NEWS OPERATIONS
JACK KING
6T-3 FWFORMATION MISSION ORGANIZATION
SPECIAL PROTOCOL COMMENTARY ACTIVITIES
PAUL HANEY CHARLES JONES BILL GREEN
MISSION
ADMINISTRATOR FOR PUBLIC AFFAIHS
-
1 JULIA
I DIRECTOR 1
10.6. LLOYD, JR 1
SCHEER 1
- D I RECTOR I INFO I
COORD I M T O R COORDINATORS COORDINATOR 1 LESGAVER I I LT* CoLCoLEMAN I 1 ALFREDFUNCH 1 CMDR. FOLEY